公开(公告)号：US07748959B1

公开(公告)日：2010-07-06

申请号：US11787559

申请日：2007-04-17

Applicant: Alex Pinera ,  Todd A. Ebert

Inventor： Alex Pinera ,  Todd A. Ebert

IPC: F01D5/08

CPC classification number: F01D5/08 ,  F02K9/48 ,  F05D2250/621 ,  F05D2300/504

Abstract: A turbine disc used in a turbo-pump that is exposed to a large thermal gradient across the sides of the rotor disc. The warm side of the turbine disc is covered by a cover plate that forms a sealed space between the turbine disc and the cover plate, and this space is evacuated or insulated to form a complete vacuum or as near as a complete vacuum as possible. The surfaces of the turbine disc and cover plate that form the vacuum space are also coated with a reflective coating such as with a highly polished surface of low emissivity in order to minimize the radiation heat loss through the vacuum space. The turbine disc can have a cover plate forming a vacuum space or insulated cavity on both sides of the turbine disc. Ribs are also used within the vacuum space as supports for the cover plate due to the difference in pressure from the ambient side and the vacuum.

Abstract translation: 在涡轮泵中使用的涡轮盘，其在转子盘的侧面上暴露于大的热梯度。 涡轮盘的温暖的一侧由盖板覆盖，该盖板在涡轮盘和盖板之间形成密封空间，并且该空间被抽空或绝缘以形成尽可能接近完全真空的完全真空。 形成真空空间的涡轮盘和盖板的表面也涂覆有诸如具有低发射率的高抛光表面的反射涂层，以便使通过真空空间的辐射热损失最小化。 涡轮盘可以具有在涡轮盘的两侧形成真空空间或绝缘腔的盖板。 由于与环境侧和真空的压力差，在真空空间内还使用肋作为盖板的支撑。

公开(公告)号：US07540709B1

公开(公告)日：2009-06-02

申请号：US11255125

申请日：2005-10-20

Applicant: Todd A. Ebert

Inventor： Todd A. Ebert

IPC: F04D29/08

CPC classification number: F01D11/02 ,  F01D5/02 ,  F01D9/041 ,  F04D29/083 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2240/55

Abstract: A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions.

Abstract translation: 一种具有带叶片和静止叶片的转子的燃气涡轮发动机，在叶片和叶片之间形成平台密封，用于阻止热气从通过涡轮机的热气流吸入涡轮机叶轮空间，平台密封件包括轴向延伸平台 在叶片和叶片上，以及从平台延伸并且在指状物和平台之间形成限制的径向延伸的指状物，以及形成在限制之间的缓冲腔，其中手指以大致径向方向布置，使得叶片能够被移除 从涡轮发动机沿径向方向，而不必首先移除叶片。 在另外的实施例中，平台密封组件可以具有在附加限制之间形成的两个或三个缓冲腔。

公开(公告)号：US07174797B2

公开(公告)日：2007-02-13

申请号：US10685339

申请日：2003-10-14

Applicant: Joseph Brostmeyer ,  Jack Wilson ,  Todd A. Ebert

Inventor： Joseph Brostmeyer ,  Jack Wilson ,  Todd A. Ebert

IPC: G01N33/00

CPC classification number: G01N25/00 ,  G01M15/14 ,  G01M99/002 ,  G01N3/18 ,  G01N17/002 ,  G01N2203/0042 ,  G01N2203/0057 ,  G01N2203/0226 ,  G01N2203/0232

Abstract: A test facility is provided for testing materials under high temperature, pressure, and mechanical loads. The facility provides a physically scaled system that simulates conditions in hot sections of gas turbine engines. A test article is coated with a test material and exposed to a hot combusting flow in a test section housing. The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow of fluid is channeled through the test article to create a sharp temperature gradient in the test article and through the test material. A liquid-cooled sleeve is disposed about the test article to create an annular channel of combusting flow over the test article. The downstream end of the second cooler flow is connected to the upstream end of the main hot flow at the combustion chamber.

Abstract translation: 提供测试设备用于在高温，高压和机械负载下测试材料。 该设施提供了一个物理尺度的系统，可模拟燃气轮机发动机热段的状况。 测试物品涂覆有测试材料并暴露于测试部分壳体中的热燃烧流。 制品可以是在流动的任何方向上定向的管道或管道构件。 流体的第二个较冷的流动通过测试物品，以在测试物品和测试材料中产生尖锐的温度梯度。 液体冷却的套筒围绕测试物品设置，以产生在测试物品上燃烧的环形通道。 第二冷却器流的下游端连接到燃烧室的主热流的上游端。

公开(公告)号：US06675872B2

公开(公告)日：2004-01-13

申请号：US10243359

申请日：2002-09-12

Applicant: Eric Lewis ,  Todd A. Ebert

Inventor： Eric Lewis ,  Todd A. Ebert

IPC: F28D1900

CPC classification number: H02K9/22 ,  F16F2222/025 ,  F28D15/0266 ,  F28D15/0275 ,  H02K7/025 ,  H02K9/20 ,  Y02E60/16 ,  Y10T74/2119

Abstract: Featured are a device, system and method for dissipating at least some heat energy generated by one or more heat generating components of a flywheel energy storage system (FESS). The method includes providing a heat pipe member, having first and second ends, and a heat dissipating member thermally engaged with the heat pipe member second end and configured to transfer heat energy therefrom. The method also includes thermally engaging the heat pipe member first end to the FESS so that at least some heat energy generated by the FESS heat generating component is communicated to the first end and thence through the heat pipe member to the heat dissipating member. Further, the method includes locating the heat dissipating member in a heat sink remote from the FESS.

Abstract translation: 特征是用于耗散由飞轮能量存储系统（FESS）的一个或多个发热部件产生的至少一些热能的装置，系统和方法。 该方法包括提供具有第一端和第二端的热管构件和与热管构件第二端热接合并且被配置为从其传热热能的散热构件。 该方法还包括将热管构件第一端热接合到FESS，使得由FESS发热部件产生的至少一些热能被传递到第一端，并且从而通过热管构件传递到散热构件。 此外，该方法包括将散热构件定位在远离FESS的散热器中。

公开(公告)号：US20160017741A1

公开(公告)日：2016-01-21

申请号：US14674261

申请日：2015-03-31

Applicant: Todd A. Ebert

Inventor： Todd A. Ebert

IPC: F01D11/02 ,  F01D5/02 ,  F01D9/04

CPC classification number: F01D11/02 ,  F01D5/02 ,  F01D9/041 ,  F04D29/083 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2240/55

Abstract: A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions.

Abstract translation: 一种具有带叶片和静止叶片的转子的燃气涡轮发动机，在叶片和叶片之间形成平台密封，用于阻止热气从通过涡轮机的热气流吸入涡轮机叶轮空间，平台密封件包括轴向延伸平台 在叶片和叶片上，以及从平台延伸并且在指状物和平台之间形成限制的径向延伸的指状物，以及形成在限制之间的缓冲腔，其中手指以大致径向方向布置，使得叶片能够被移除 从涡轮发动机沿径向方向，而不必首先移除叶片。 在另外的实施例中，平台密封组件可以具有在附加限制之间形成的两个或三个缓冲腔。

公开(公告)号：US08240986B1

公开(公告)日：2012-08-14

申请号：US12004950

申请日：2007-12-21

Applicant: Todd A. Ebert

Inventor： Todd A. Ebert

IPC: F04D29/08

CPC classification number: F01D11/001 ,  F01D11/025 ,  F05D2240/56

Abstract: A turbine inter-stage seal with active clearance control. The inner diameter of the stator vane includes a seal support structure with a plurality of segmented seal supports each movable by an actuator located on the vane outer diameter with a plunger or push rod extending through the hollow portion of the vanes. A segmented seal arrangement, such as segmented brush seals, are secured to the underside of the seal support segments and form a complete annular seal for the inter-stage between adjacent rotor disks. A proximity probe or microwave sensor detects the brush seal clearance, and a controller regulates the brush seal clearance.

Abstract translation: 具有主动间隙控制的涡轮级间密封。 定子叶片的内径包括具有多个分段密封支撑件的密封支撑结构，每个分段密封支撑件可由位于叶片外径上的致动器通过延伸穿过叶片的中空部分的柱塞或推杆移动。 诸如分段刷密封件的分段密封装置固定到密封支撑段的下侧，并且形成用于相邻转子盘之间的级间的完整的环形密封件。 接近探针或微波传感器检测刷密封间隙，控制器调节刷密封间隙。

公开(公告)号：US07445424B1

公开(公告)日：2008-11-04

申请号：US11409925

申请日：2006-04-22

Applicant: Todd A. Ebert ,  Alex Pinera ,  Antonio Negron

Inventor： Todd A. Ebert ,  Alex Pinera ,  Antonio Negron

IPC: F01D11/04

CPC classification number: F01D11/001 ,  F01D5/081 ,  F05D2240/56 ,  F05D2260/14 ,  F05D2300/50212 ,  F16J15/3288

Abstract: In a gas turbine engine having a rim cavity formed between a rotor disk and a stator, and a brush seal or other seal member providing an airflow seal between the stator and a side plate of the rotor disk, a thermally responsive valve device is located in the bypass passage of the stator to form a parallel air flow path with the brush seal. As the brush seal wears and the leakage airflow around the worn brush seal increases, the air flow temperature in the rim cavity would decrease. The thermally responsive valve device would detect the decreasing airflow temperature, and reduce the airflow passing through the bypass passage in order to prevent the temperature of the rim cavity from decreasing. The temperature responsive valve device makes use of a bimetallic valve member that regulates airflow based upon temperature.

Abstract translation: 在具有形成在转子盘和定子之间的边缘空腔的燃气涡轮发动机中，以及在定子和转子盘的侧板之间提供气流密封的刷密封件或其他密封构件，热响应阀装置位于 定子的旁路通道与刷密封件形成平行的空气流动路径。 当刷子密封件磨损并且磨损的刷密封件周围的泄漏气流增加时，轮辋腔中的空气流动温度将降低。 热响应阀装置将检测气流温度的降低，并且减少通过旁路通道的气流，以防止边缘腔的温度降低。 温度响应阀装置利用基于温度来调节气流的双金属阀构件。